WO2020042983A1 - Hélice, ensemble de puissance et véhicule aérien sans pilote - Google Patents

Hélice, ensemble de puissance et véhicule aérien sans pilote Download PDF

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Publication number
WO2020042983A1
WO2020042983A1 PCT/CN2019/101799 CN2019101799W WO2020042983A1 WO 2020042983 A1 WO2020042983 A1 WO 2020042983A1 CN 2019101799 W CN2019101799 W CN 2019101799W WO 2020042983 A1 WO2020042983 A1 WO 2020042983A1
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WO
WIPO (PCT)
Prior art keywords
propeller
hub
blade
center
chord length
Prior art date
Application number
PCT/CN2019/101799
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English (en)
Chinese (zh)
Inventor
张海浪
孙维
罗东东
Original Assignee
深圳市道通智能航空技术有限公司
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Publication of WO2020042983A1 publication Critical patent/WO2020042983A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/20—Constructional aspects of UAVs for noise reduction

Definitions

  • the invention relates to the technical field of unmanned aerial vehicles, in particular to a propeller, a power component and an unmanned aerial vehicle using the power component.
  • UAV is a kind of unmanned aerial vehicle that controls flight attitude through radio remote control equipment and built-in programs. It has been widely used in military and civilian fields.
  • the propeller is an important part of the drone and the main source of power for hovering and maneuvering.
  • the aerodynamic efficiency of the propeller directly affects the hover time of the drone.
  • the hovering time of industrial-grade drones in turn restricts the drone's range and task execution time; the hovering time of consumer-grade drones will also affect the user experience.
  • the aerodynamic efficiency of the drone's propeller is not high, resulting in a short hovering time of the drone, which cannot meet the actual use requirements.
  • the propeller rotates noise will be generated.
  • the noise of the propeller becomes the main source of drone noise. It not only pollutes the surrounding airspace environment, but these noises will propagate to the drone's fuselage, causing The vibration of the man-machine body seriously affects the flight safety of the drone.
  • propellers with high aerodynamic efficiency and low noise levels are essential for drones.
  • the technical problem solved by the present invention is to provide a propeller, a power component and an unmanned aerial vehicle with high aerodynamic efficiency and low noise level, which can effectively overcome the defects in the prior art, improve the aerodynamic efficiency of the propeller, and reduce its noise level. , Thereby effectively extending the hovering time of the drone, at the same time reducing the noise level of the drone, improving the flight safety of the drone, and improving the user comfort.
  • the present invention provides a propeller, including a propeller hub and a propeller blade connected to the propeller hub, the propeller blade includes a propeller root and a propeller tip facing away from the propeller root, and the propeller blade has Blade surface, blade back, leading edge connecting the blade surface and one side of the blade back, and trailing edge connecting the blade surface and the other side of the blade back, the radius of the hub is r, and the propeller Has a radius of R, where:
  • the paddle is in the shape of a willow leaf
  • the ratio of the chord length to the diameter of the propeller is 9.5% ⁇ 0.3%;
  • the ratio of the chord length to the diameter of the propeller is 12.3% ⁇ 0.1%;
  • the ratio of the chord length to the diameter of the propeller is 10.9% ⁇ 0.1%.
  • the blade has a central axis, and the leading and trailing edges are symmetrical with respect to the central axis.
  • chord length distribution of the blade near the blade tip is oval.
  • chord length is 20 ⁇ 0.3mm
  • chord length is 26 ⁇ 0.3mm
  • chord length is 23 ⁇ 0.3 mm.
  • the ratio of the chord length to the propeller diameter at a position 10% ⁇ R from the center of the propeller hub is 7.1% ⁇ 0.5%.
  • chord length is 15 ⁇ 0.5mm.
  • the ratio of the chord length to the diameter of the propeller is 8.5% ⁇ 0.1% at a position 85% ⁇ R from the center of the hub.
  • the chord length is 18 ⁇ 0.3 mm.
  • the ratio of the chord length to the diameter of the propeller is 1.9% ⁇ 0.1%.
  • the chord length is 4 ⁇ 0.3 mm.
  • the maximum chord length of the blade is at a position 50% ⁇ R from the center of the hub.
  • the twist angle of the blade is 25 ° ⁇ 0.3 °;
  • the twist angle of the blade is 19 ° ⁇ 0.5 °;
  • the twist angle of the blade is 14 ° ⁇ 0.5 °.
  • the twist angle of the blade is 13 ° ⁇ 0.5 ° from a position r to 10% ⁇ R from the center of the hub.
  • the twist angle of the blade is 12 ° ⁇ 0.5 °.
  • the twist angle of the blade is 10 ° ⁇ 0.5 °.
  • the relative thickness of the airfoil of the blade is 11% ⁇ 0.5% at a position r-30% ⁇ R from the center of the hub;
  • the relative thickness of the airfoil of the blade at a position 30% ⁇ R to 75% ⁇ R from the center of the hub is 7.1% ⁇ 0.3%;
  • the relative thickness of the airfoil of the blade is 5.2% ⁇ 0.3% at a position 75% ⁇ R to 100% ⁇ R from the center of the hub;
  • the relative thickness of the airfoil is a ratio of the thickness of the airfoil of the blade to the chord length of the airfoil.
  • the position of the maximum thickness in the relative thickness of the airfoil of the blade is a chord length 27.5% ⁇ 0.5% from the leading edge ;
  • the maximum thickness position of the relative thickness of the airfoil of the blade is a chord length 18% ⁇ 0.3% from the leading edge;
  • the maximum thickness position in the relative thickness of the airfoil of the blade is a chord length 23% ⁇ 0.3% from the leading edge.
  • the relative camber of the airfoil of the blade is 5% ⁇ 0.5%
  • the relative camber of the blade airfoil at a position 30% ⁇ R to 75% ⁇ R from the center of the hub is 5.8% ⁇ 0.3%;
  • the relative camber of the airfoil of the blade at a position 75% ⁇ R to 100% ⁇ R from the center of the hub is 4.5% ⁇ 0.3%;
  • the relative camber of the airfoil is a ratio of the camber of the mid-arc of the airfoil of the blade to the chord length.
  • the position of the maximum camber in the relative camber of the airfoil of the blade at a position r-30% ⁇ R from the center of the hub is 38.5% ⁇ 0.5% chord length from the leading edge;
  • the position of the maximum camber in the relative camber of the airfoil of the blade is a chord length of 43.5% ⁇ 0.3% from the leading edge;
  • the position of the maximum camber in the relative camber of the airfoil of the blade is a chord length of 22.5% ⁇ 0.3% from the leading edge.
  • the Reynolds number of the propeller ranges from 10 4 to 5 ⁇ 10 5 .
  • the present invention further provides a power assembly, which includes a motor and a propeller as described above, and a hub of the propeller is connected to an output shaft of the motor.
  • the present invention also provides an unmanned aerial vehicle, which includes: a fuselage, a boom connected to the fuselage, and the above-mentioned power component mounted on the boom.
  • the present invention can effectively ensure that the blade has the best working performance by setting specific airfoil distribution, torsion angle distribution and chord length distribution for the propeller blade, and setting the blade into a willow shape. , Can effectively improve the aerodynamic efficiency of the propeller and reduce its noise level. Further, the application of the propeller to power components and drones can correspondingly improve the efficiency of power components and drones, thereby effectively extending the hovering time of the drone, while reducing the noise level of the drone and improving the drone. Human-machine flight safety and improve user comfort.
  • FIG. 1 is a perspective structural view of an embodiment of a drone according to the present invention
  • FIG. 2 is a schematic perspective view of a power component of the drone shown in FIG. 1;
  • FIG. 2 is a schematic perspective view of a power component of the drone shown in FIG. 1;
  • FIG. 3 is a schematic perspective view of a propeller in the power assembly shown in FIG. 2;
  • FIG. 4 is a front view of the propeller shown in FIG. 3;
  • FIG. 5 is a top view of the propeller shown in FIG. 3;
  • FIG. 6 is a right side view of the propeller shown in FIG. 3;
  • FIG. 7 is a cross-sectional view of a blade in the propeller shown in FIG. 3, which shows various parameters related to the airfoil of the blade.
  • 100-unmanned aerial vehicle 40-airframe, 50-airframe;
  • the propeller provided by the embodiment of the present invention is a motor with high aerodynamic efficiency.
  • the propeller is mounted on the motor, and can be applied to any application field of mechatronics, especially to various movable objects driven by the motor. Including, but not limited to, unmanned aerial vehicles (UAVs), ships, and robots.
  • UAVs unmanned aerial vehicles
  • a drone is taken as an example for description. Applying the propeller provided in the embodiment of the present invention to a drone can effectively extend the hovering time of the drone.
  • FIG. 1 is a schematic structural diagram of a drone provided by one embodiment of the present invention.
  • the structure of the drone 100 includes a fuselage 40, four arms 50 extending from the fuselage 40, and a power assembly 30 mounted on each of the arms 50. That is, the drone 100 of the present invention is a four-rotor drone, and the number of power components 30 is four.
  • the drone 100 may be any other suitable type of rotor drone, such as a dual-rotor drone, a six-rotor drone, or the like.
  • the power module 30 is applied to other types of unmanned aerial vehicles, the number of the power modules 30 may be changed according to actual needs, which is not limited in the embodiment of the present invention.
  • the drone 100 may further include a gimbal (not shown), which is connected to the fuselage 40 and is located at the bottom of the fuselage 40.
  • the gimbal is used to carry a high-definition digital camera or other video cameras.
  • the device is used to eliminate the disturbance of the high-definition digital camera or other camera device, and to ensure that the video captured by the camera or other camera device is clear and stable.
  • the arm 50 is fixedly connected to the body 40.
  • the arm 50 is integrally formed with the body 40.
  • the arm 50 may also be connected to the fuselage 40 in a manner of being unfolded or folded relative to the fuselage 40.
  • the arm 50 may be connected to the main body 40 through a rotating shaft mechanism, so that the arm 50 can be unfolded or folded relative to the main body 40.
  • the power assembly 30 includes a motor 20 and a propeller 10 driven by the motor 20.
  • the propeller 10 is installed on an output shaft of the motor 20, and the propeller 10 rotates under the driving of the motor 20. To generate lift or thrust that makes the drone 100 fly.
  • the motor 20 may be any suitable type of motor, such as a brushed motor, a brushless motor, a DC motor, a stepper motor, an AC induction motor, and the like.
  • the power assembly 30 of the present invention further includes an electronic governor (not shown) disposed in a cavity formed by the fuselage 40 or the arm 50, and the electronic governor is used for generating The throttle signal generates a motor control signal for controlling the motor speed to obtain the flying speed or attitude required by the drone.
  • the throttle controller or the throttle generator may be a flight control module of the drone.
  • the flight control module senses the environment around the drone through various sensors and controls the flight of the drone.
  • the flight control module may be a processing module (Application Unit), an Application Specific Integrated Circuit (ASIC), or a Field Programmable Gate Array (FPGA).
  • the drone's flight control module sends a throttle signal to the ESC, and the ESC receives the throttle signal, generates and sends it to the motor for The motor performs motor control signals such as starting and controlling the rotation speed of the motor.
  • the propeller 10 includes a hub 1 and at least two blades 2 connected to the hub 1 (the two blades are taken as an example in the figure).
  • the blade 2 includes a blade root 110 and a blade tip 120 facing away from the blade root 110.
  • the blade 2 has a leading edge a and a trailing edge b.
  • the at least two blades 2 are fixedly connected to the hub 1.
  • the at least two blades 2 are integrally formed with the hub.
  • the at least two blades 2 may also be connected to the hub 1 in a manner of being unfolded or folded relative to the hub 1.
  • the at least two blades 2 may be connected to the hub 1 through a rotating shaft, respectively, so as to achieve the expansion or folding of the at least two blades 2 relative to the hub 1.
  • the hub 1 is used to fixedly connect the propeller 10 to an output shaft of the motor 20.
  • the propeller hub 1 is provided with internal threads, and the output shaft of the motor 20 is provided with external threads corresponding to the internal threads. Through the cooperation of the internal and external threads, The screw connection between the propeller 10 and the motor 20 is realized.
  • the output shaft of the motor 20 may also be locked in the propeller hub 1 by a screw lock, or the output shaft of the motor 20 and the propeller hub 1 may be connected by means of a knurled centimeter.
  • a groove may be provided on the motor 20, and a claw portion matching the groove is provided on the propeller 10.
  • the propeller 10 is rotationally connected to the motor 20, and is connected to the motor 20 through the claw portion on the propeller 10. The clamping of the upper groove realizes the connection between the propeller 10 and the motor 20.
  • FIG. 3 is a schematic perspective view of the propeller 10 in the power assembly shown in FIG. 2;
  • FIG. 4 is a front view of the propeller 10 shown in FIG. 3;
  • FIG. 5 is a right side view of the propeller 10 shown in FIG. 3;
  • a cross-sectional view of the blade 2 in the propeller 10 shown in FIG. 7 shows various parameters related to the airfoil of the blade 2;
  • FIG. 7 is a top view of the propeller 10 shown in FIG. 3.
  • the propeller 10 provided by the embodiment of the present invention can effectively ensure that the blade 2 has an optimal blade shape by improving the chord length distribution, twist angle distribution and airfoil distribution of the blade 2 and setting the blade 2 into a willow shape.
  • the working performance can effectively improve the aerodynamic efficiency of the propeller 10 and reduce its noise level.
  • applying the propeller 10 to the power module 30 and the drone 100 can correspondingly improve the efficiency of the power module 30 and the drone 100, thereby further effectively extending the hovering time of the drone 100 and reducing the drone.
  • the noise level of 100 improves the flight safety of the drone 100 and improves the user comfort.
  • improvements in size of the blade 2 of the propeller 10 provided by the embodiment of the present invention will be described from the aspects of the overall shape, chord length, twist angle, and airfoil distribution of the blade.
  • the propeller 10 provided by the present invention is in a willow shape.
  • the propeller 10 has a central axis (indicated by a dotted line in the middle of the blade 2 in the figure), and the leading edge a and the trailing edge b of the blade 2 are substantially symmetrical with respect to the central axis.
  • the chord length distribution of the blade 2 near the blade tip 120 is substantially elliptical.
  • the elliptical end ie, the tip of the blade 2 is cut.
  • the ellipse at the blade tip 120 is beneficial to reduce the intensity of the blade tip vortex, and further reduce the propeller vortex interference effect of the propeller 10 to reduce the noise generated by the propeller 10.
  • the "willow" shape of the blade 2 gradually shrinks at the blade tip 120, which can reduce the lateral flow of the airflow and improve the aerodynamic efficiency of the propeller.
  • the radius of the hub 1 of the propeller 10 is r, and the radius of the propeller 10 is R. Therefore, it can be estimated that the total length of the blade 2 of the propeller 10 is R-r.
  • the distance from any section on the blade 2 to the center of the hub 1 is represented by L2; the chord length at any section on the blade 2 is represented by L1, and the chord length L1 refers to the length of the chord line l at the section, the chord line l refers to the line connecting the leading edge a of the blade 2 at the leftmost end point in the section and the trailing edge b at the rightmost end point in the section.
  • a series of inscribed circles tangent to the upper and lower arcs are made inside the airfoil.
  • the line connecting the centers of the circles is called the middle arc of the airfoil.
  • the diameter of the largest inscribed circle is called the thickness of the airfoil. t.
  • the maximum distance between the middle arc line m and the chord line l is called the camber f of the airfoil, and the airfoil with zero camber f is called the symmetrical airfoil, where the arc and the chord line coincide.
  • the relative thickness of the airfoil is defined as the ratio of the thickness of the airfoil t to the chord length L1, that is, t / L1;
  • the relative camber of the airfoil is defined as the ratio of the curvature f of the airfoil to the chord length L1, that is, f / L1 .
  • twist angle ⁇ also known as the twist angle or blade angle, refers to the angle between the chord line l of the propeller 10 and the rotation plane of the propeller 10, and its variation law is one of the main factors affecting the working performance of the propeller.
  • the ratio of the chord length L1 at a plurality of sections in the blade 2 of the drone 100 to the diameter of the propeller 10 is set, in which the distance from the center of the propeller hub 30% ⁇ R, 50%
  • the improvement of the ratio of the chord length L1 at the cross section of ⁇ R and 75% ⁇ R to the diameter of the propeller 10 has the best effect.
  • the ratio of the chord length L1 of the blade 2 to the diameter 2R of the propeller is set as follows:
  • the ratio of the chord length L1 to the diameter 2R of the propeller is 9.5% ⁇ 0.3%;
  • the ratio of the chord length L1 to the diameter 2R of the propeller is 12.3% ⁇ 0.1%;
  • the ratio of the chord length L1 to the diameter 2R of the propeller is 10.9% ⁇ 0.1%.
  • chord lengths at the positions of 10% ⁇ R, 85% ⁇ R, and 100% ⁇ R from the center of the hub are respectively improved, which can further improve the aerodynamic efficiency and reduce the noise of the propeller 10 Level, thereby further extending the hovering time of the drone 100 and reducing the noise of the drone 100.
  • the ratio of the chord length L1 to the propeller diameter 2R is 7.1% ⁇ 0.5%.
  • the ratio of the chord length L1 to the diameter 2R of the propeller is 8.5% ⁇ 0.1% from the center of the propeller at a location 85% ⁇ R.
  • the ratio of the chord length L1 to the diameter 2R of the propeller is 1.9% ⁇ 0.1%.
  • the maximum chord length of the blade is at a position 50% ⁇ R from the center of the hub.
  • the radius R of the propeller is preferably 100 mm to 150 mm
  • chord length is 20 ⁇ 0.3mm
  • chord length is 26 ⁇ 0.3mm
  • chord length is 23 ⁇ 0.3 mm.
  • the chord length is 15 ⁇ 0.5mm.
  • the chord length is 18 ⁇ 0.3 mm.
  • the chord length is 4 ⁇ 0.3 mm.
  • the embodiment of the present invention provides a specific propeller.
  • the radius R of the propeller is 105 mm
  • the radius r of the propeller is 6.75 mm
  • the length of the blade is optionally 98.25 mm.
  • the chord length is 20mm; at a position of 52.5mm from the hub center, the chord length is 26mm; at a position of 78.5mm from the hub center, The chord length is 23mm.
  • the chord length is 15 mm.
  • the chord length is 18 mm.
  • the chord length is 4 mm.
  • the torsion angles at multiple sections in the blade 2 of the drone 100 are improved, where at 30% ⁇ R, 50% ⁇ R, and 75% ⁇ R sections from the center of the hub
  • the improvement of the twist angle has the best effect.
  • the twist angle ⁇ parameter of the blade 2 is set as follows:
  • the twist angle of the blade 2 is 25 ° ⁇ 0.3 °;
  • the twist angle of the blade 2 is 19 ° ⁇ 0.5 °;
  • the twist angle of the blade 2 is 14 ° ⁇ 0.5 °.
  • the setting of the twist angle of the blade 2 can effectively ensure that the blade 2 has the best working performance, can effectively improve the aerodynamic efficiency of the propeller 10 and reduce its noise level, thereby further extending the hovering time of the drone 100 and reducing The noise of the drone 100.
  • the twist angles of the blades 2 in the sections r to 10% ⁇ R, 85% ⁇ R, and 100% ⁇ R from the center of the hub are improved, respectively, and the aerodynamic efficiency of the propeller 10 can be further improved And reduce its noise level, thereby further extending the hovering time of the drone 100 and reducing the noise of the drone 100.
  • the twist angle of the blade 2 is 13 ° ⁇ 0.5 °;
  • the twist angle of the blade 2 is 12 ° ⁇ 0.5 °;
  • the twist angle of the blade 2 is 10 ° ⁇ 0.5 °.
  • the embodiment of the present invention provides a specific propeller.
  • the radius R of the propeller is 105mm
  • the radius r of the propeller is 6.75mm
  • the length of the blade is optionally 98.25mm.
  • the twist angle of the blade is 25 °; at a position of 52.5mm from the center of the hub, the blade twist angle is 19 °; at a position from the hub At a position of 78.75 mm in the center, the twist angle of the blade is 14 °.
  • the twist angle of the blade is 13 ° at a position from 6.75 mm to 10.5 mm from the center of the blade hub.
  • the twist angle of the blade is 12 °. Further preferably, at a position 105 mm from the center of the propeller hub, the twist angle of the propeller blade is 10 °.
  • the relative thickness of the airfoil of the blade 2 is set as follows:
  • the relative thickness of the airfoil of the blade 2 is 11% ⁇ 0.5% at a position r-30% ⁇ R from the center of the hub;
  • the relative thickness of the airfoil of the blade 2 at a position 30% ⁇ R to 75% ⁇ R from the center of the hub is 7.1% ⁇ 0.3%;
  • the relative thickness of the airfoil of the blade 2 at a position 75% ⁇ R to 100% ⁇ R from the center of the hub is 5.2% ⁇ 0.3%.
  • L2 is the distance from the center of the propeller, at a position r-30% ⁇ R from the center of the propeller, that is, when L2 is r to 30% of the radius of the propeller ; At a distance of 30% ⁇ R ⁇ 75% ⁇ R from the center of the hub, that is, L2 is 30% of the radius length of the propeller 10 to 75% of the radius length of the propeller 10; The position of% ⁇ R to 100% ⁇ R, that is, when L2 is 75% of the radius length of the propeller 10 to 100% of the radius length of the propeller 10.
  • the maximum thickness position of the relative thickness of the airfoil of the blade 2 is a distance (27.5%) from the leading edge a ⁇ 0.5%) ⁇ chord length L1; at a position 30% ⁇ R ⁇ 75% ⁇ R from the center of the hub, the maximum thickness position of the relative thickness of the airfoil of the blade 2 is spaced from the leading edge a (18% ⁇ 0.3%) chord length; at a position 75% ⁇ R ⁇ 100% ⁇ R from the center of the hub, the maximum thickness position of the relative thickness of the airfoil of the blade 2 is the same as the leading edge a Distance (23% ⁇ 0.3%) x chord length L1.
  • the above-mentioned preferred maximum relative airfoil thickness can effectively ensure the aerodynamic efficiency of the blade 2 and reduce its noise level, thereby further extending the hovering time of the drone 100 and reducing the noise of the drone 100.
  • an embodiment of the present invention provides a specific propeller.
  • the radius R of the propeller is 105 mm
  • the radius r of the propeller is 6.75 mm
  • the length of the blade is optionally 98.25 mm.
  • the relative thickness of the airfoil of the blade is 11% at a position of 6.75mm to 31.5mm from the center of the hub; the relative thickness of the airfoil of the blade at a position of 31.5mm to 78.75mm from the center of the hub It is 7.1%; at a position from 78.75mm to 105mm from the center of the hub, the relative thickness of the airfoil of the blade is 5.2%.
  • the relative camber of the airfoil of the blade 2 is set as follows:
  • the relative camber of the airfoil of the blade 2 is 5% ⁇ 0.5% at a position r-30% ⁇ R from the center of the hub;
  • the relative camber of the airfoil 2 is 4.5% ⁇ 0.3%.
  • the position of the maximum camber in the relative camber of the airfoil of the blade 2 at a position r-30% from the center of the hub is the distance from the leading edge a (38.5%).
  • chord length L1 at a position 30% ⁇ R ⁇ 75% ⁇ R from the center of the hub, the maximum camber position in the relative camber of the airfoil of the blade 2 is a distance from the leading edge a (43.5% ⁇ 0.3%) ⁇ chord length L1; at a position 75% ⁇ R ⁇ 100% ⁇ R from the center of the hub, the position of the maximum camber in the relative camber of the airfoil of the blade 2 is the leading edge a Distance (22.5% ⁇ 0.3%) x chord length L1.
  • the above-mentioned preferred maximum relative camber can also further improve the aerodynamic efficiency of the propeller 10 and reduce its noise level, thereby further extending the hovering time of the drone 100 and reducing the noise of the drone 100.
  • an embodiment of the present invention provides a specific propeller.
  • the radius R of the propeller is 105 mm
  • the radius r of the propeller is 6.75 mm
  • the length of the blade is optionally 98.25 mm.
  • the relative camber of the airfoil of the blade is 5%; at a position of 31.5mm to 78.75mm from the center of the hub, the relative camber of the airfoil of the blade It is 5.8%; at a position from 78.75mm to 105mm from the center of the hub, the relative camber of the blade is 4.5%.
  • the above technical solution is applicable to a propeller having a Reynolds number in a range of 10 4 to 5 ⁇ 10 5 .
  • the blades can effectively ensure the best working performance of the blades and can effectively Improve the aerodynamic efficiency of the propeller and reduce its noise level. Further, the application of the propeller to power components and drones can correspondingly improve the efficiency of power components and drones, thereby effectively extending the hovering time of the drone, while reducing the noise level of the drone and improving the drone. Human-machine flight safety and improve user comfort.

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  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne une hélice, un ensemble de puissance et un véhicule aérien sans pilote. L'hélice (10) comprend un moyeu d'hélice (1) et une pale d'hélice (2) raccordée au moyeu d'hélice (1). La pale d'hélice (2) comprend une emplanture de pale (110) et une extrémité de pale (120) disposée à distance de l'emplanture de pale (110). La pale d'hélice (2) possède un bord d'attaque (a) et un bord de fuite (b). Le rayon du moyeu d'hélice (1) est r, et le rayon de l'hélice (10) est R, la pale d'hélice (2) ayant la forme d'une feuille de saule. Dans une position de 30 % x R à partir du centre du moyeu d'hélice (1), le rapport d'une longueur de corde sur le diamètre de l'hélice (10) est de 9,5 % ± 0,3 %. Dans une position de 50 % x R à partir du centre du moyeu d'hélice (1), le rapport d'une longueur de corde sur le diamètre de l'hélice (10) est de 12,3 % ± 0,1 %. Dans une position de 75 % x R à partir du centre du moyeu d'hélice (1), le rapport d'une longueur de corde sur le diamètre de l'hélice (10) est de 10,9 % ± 0,1 %. La distribution de longueur de corde, la distribution d'angle de torsion et la distribution de profil aérodynamique sont spécifiquement conçues dans l'invention, et la pale d'hélice (2) a la forme d'une feuille de saule de façon à garantir efficacement que la pale d'hélice (2) a une performance de fonctionnement optimale, améliorer efficacement l'efficacité aérodynamique de l'hélice (10), et réduire le bruit de l'hélice (10).
PCT/CN2019/101799 2018-08-28 2019-08-21 Hélice, ensemble de puissance et véhicule aérien sans pilote WO2020042983A1 (fr)

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CN201821401883.7U CN209241318U (zh) 2018-08-28 2018-08-28 螺旋桨、动力组件及无人机

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CN209241318U (zh) * 2018-08-28 2019-08-13 深圳市道通智能航空技术有限公司 螺旋桨、动力组件及无人机

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